Research Papers: Gas Turbines: Aircraft Engine

First and Second Law Analysis of Future Aircraft Engines

[+] Author and Article Information
Tomas Grönstedt

e-mail: tomas.gronstedt@chalmers.se

Oskar Thulin

Chalmers University of Technology,
Gothenburg SE-41296, Sweden

Anders Lundbladh

GKN Aerospace,
Trollhättan SE-46181, Sweden

1Corresponding author.

Contributed by the Aircraft Engine Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 9, 2013; final manuscript received August 7, 2013; published online November 19, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(3), 031202 (Nov 19, 2013) (10 pages) Paper No: GTP-13-1249; doi: 10.1115/1.4025727 History: Received July 09, 2013; Revised August 07, 2013

An optimal baseline turbofan cycle designed for a performance level expected to be available around year 2050 is established. Detailed performance data are given in take-off, top of climb, and cruise to support the analysis. The losses are analyzed, based on a combined use of the first and second law of thermodynamics, in order to establish a basis for a discussion on future radical engine concepts and to quantify loss levels of very high performance engines. In light of the performance of the future baseline engine, three radical cycles designed to reduce the observed major loss sources are introduced. The combined use of a first and second law analysis of an open rotor engine, an intercooled recuperated engine, and an engine working with a pulse detonation combustion core is presented. In the past, virtually no attention has been paid to the systematic quantification of the irreversibility rates of such radical concepts. Previous research on this topic has concentrated on the analysis of the turbojet and the turbofan engine. In the developed framework, the irreversibility rates are quantified through the calculation of the exergy destruction per unit time. A striking strength of the analysis is that it establishes a common currency for comparing losses originating from very different physical sources of irreversibility. This substantially reduces the complexity of analyzing and comparing losses in aero engines. In particular, the analysis sheds new light on how the intercooled recuperated engine establishes its performance benefits.

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Grahic Jump Location
Fig. 1

Exergy balance applied to a moving system

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Fig. 2

SFC development trends [15]

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Fig. 3

A schematic overview of the intercooled recuperated concept [33]. The abbreviations used are: IC = intercooler, REC = recuperator, and VGV = variable low pressure turbine guide vane.

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Fig. 4

The open rotor engine (image: Chalmers University)

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Fig. 5

Conceptual illustration of a pulse detonation core (image: Chalmers University)




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